An improved game washer is compatible with a variety of receptacles and includes one or more cradles for receiving and holding various types of game. Agitation for washing game is provided via one or more water flows at one or more outlets of an agitator. An outlet engages a bottom of a cradle to provide water flow at the cradle. The agitator extends out of an opening of a receptacle at a central portion thereof to receive a water supply, while forming a gap at the opening to permit a flow of water and waste material out of the receptacle.

A method of manufacturing a de-icer assembly includes disposing a first welded-material layer and a second welded-material layer beneath a horn of a horn-based welding system, controlling the horn to move along a welded-portion pattern configured to weld the first welded-material layer to the second welded-material layer in the pattern of the welded-portion pattern such that inflatable portions are formed within the welded-portion pattern formed in the de-icer assembly between non-welded sections of the first welded-material layer and the second welded-material layer, and applying high-frequency energy to the first welded-material layer and a second welded-material layer using the horn such that the first welded-material layer and the second welded-material layer are welded together at areas in the shape of the welded-portion pattern to form a welded de-icer assembly.

A die-welding system for a de-icer assembly includes a die, a die base, a high energy source, and a de-icer assembly. The de-icer assembly includes a first welded-material layer and a second welded-material layer. At least one of the die and the die base includes a welded-portion pattern thereon configured to weld the first welded-material layer to the second welded-material layer in the pattern of the welded-portion pattern such that inflatable portions are formed within the welded-portion pattern formed in the de-icer assembly between non-welded sections of the first welded-material layer and the second welded-material layer.

A method of manufacturing a de-icer assembly includes positioning a first welded-material layer and a second welded-material layer between a die and a die base of a die-based welding system, wherein at least one of the die and the die base includes a welded-portion pattern configured to weld the first welded-material layer to the second welded-material layer in the pattern such that inflatable portions are formed within the welded-portion pattern formed in the de-icer assembly between non-welded sections of the first welded-material layer and the second welded-material layer, pressing the first welded-material layer and the second welded-material layer together between the die and die base, and applying high energy to the die-based welding system using a high energy source such that the first welded-material layer and the second welded-material layer are welded together at the areas in the shape of the welded-portion pattern to form a welded de-icer assembly.

The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

A blade for a rotor of a hover-capable aircraft is described comprising: a main body with a first outer surface; and a de-icing system for removing ice; the de-icing system, in turn, comprises: a first layer formed by a shape-memory material activatable so as to alter its shape according to a temperature-associable quantity, which is arranged on at least one outer surface of the main body; the de-icing system is characterized in that it comprises a second covering layer, which defines at least a portion of a second outer surface of the blade on which ice deposits; the second layer laid on top of the first layer on the opposite side of the main body is selectively movable under the action of the first layer so as to exert a mechanical action on the ice and remove it from the blade, and is adapted to protect the first layer from external agents.

A blade for a rotor of a hover-capable aircraft is described comprising: a main body with a first outer surface; and a de-icing system for removing ice; the de-icing system, in turn, comprises: a first layer formed by a shape-memory material activatable so as to alter its shape according to a temperature-associable quantity, which is arranged on at least one outer surface of the main body; the de-icing system is characterized in that it comprises a second covering layer, which defines at least a portion of a second outer surface of the blade on which ice deposits; the second layer laid on top of the first layer on the opposite side of the main body is selectively movable under the action of the first layer so as to exert a mechanical action on the ice and remove it from the blade, and is adapted to protect the first layer from external agents.

A coaxial pressure lock assembly of an aircraft door, the coaxial pressure lock assembly comprises a pressure panel positioned adjacent an opening formed in the aircraft door such that the pressure panel is seated in the opening when the pressure panel is in a closed position, and a latch shaft extending through a clevis of the pressure panel. The latch shaft is configured to rotate about a latch shaft rotational axis extending through the latch shaft. The pressure panel is rotatable between the closed position and an open position about the latch shaft rotational axis. The latch shaft is a portion of a latch assembly configured to allow or prevent unlatching the aircraft door.

De-icing processes and products with coatings enabling de-icing are disclosed. The de-icing process includes mechanically removing ice from a coated article having a chemical vapor deposition coating. The chemical vapor deposition coating includes silicon, carbon, and fluorine. The chemical vapor deposition coating is hydrophobic and oleophobic. The chemical vapor deposition coating remains hydrophobic and oleophobic after the mechanically removing of the ice. The product is a coated article having a chemical vapor deposition coating and ice on the chemical vapor deposition coating. The chemical vapor deposition coating includes silicon, carbon, and fluorine. The chemical vapor deposition coating is hydrophobic and oleophobic. The chemical vapor deposition coating remains hydrophobic and oleophobic in response to mechanically removing of the ice on the chemical vapor deposition coating.